CN110979649A

CN110979649A - Braking differential type rotor propeller fixed wing helicopter

Info

Publication number: CN110979649A
Application number: CN202010056600.5A
Authority: CN
Inventors: 江富余
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-01-18
Filing date: 2020-01-18
Publication date: 2020-04-10

Abstract

A braking differential type gyroplane with fixed wings is composed of two rotary wings arranged on small wing towers at head and tail of helicopter body, the blades of rotary wings connected to said rotary wings via their wings, total pitch and periodic pitch controllers, single-wing fixed wings with high aspect ratio, variable-pitch propellers arranged at left and right sides of fixed wings, engine for driving differential mechanism via speed variator and clutch, overrunning clutch, universal shaft and synchronous rotor-rotator for driving two rotary wings, wheel-type undercarriage, and braking differential mechanism for distributing power to rotary wings or variable-pitch propellers, The fixed wing and the autorotation rotor wing have various flight modes, have high speed and low energy consumption and are suitable for the occasions requiring the take-off and landing of airport.

Description

Braking differential type rotor propeller fixed wing helicopter

Technical Field

The invention relates to a braking differential type rotor propeller fixed wing helicopter which can be pulled by propellers, can fly forwards by airport sliding, and can also fly forwards, backwards, leftwards and rightwards without depending on the vertical lifting, hovering and multi-rotor wing adopted in an airport.

Background

The prior known successful method for realizing the helicopter which can fly before sliding away in an airport and can also fly all around without depending on the vertical lifting and hovering of a plurality of rotors in the airport is a tilting rotor aircraft.

Disclosure of Invention

In order to improve the efficiency of a rotor wing, reduce the high requirement on the strength of a wing beam, realize the high efficiency of vertical lifting of a rotor wing helicopter and the high speed of horizontal flight of a fixed wing, the invention provides a braking differential type rotor wing propeller fixed wing helicopter, and the aim is realized.

The technical scheme adopted by the invention for solving the technical problems is as follows: two rotors adopt the tandem type overall arrangement, and the fuselage head sets up a wing section tower, and the tower plays the effect of vertical fin, and this tower is called first tower below as, sets up first rotor on first tower, and the fuselage afterbody sets up a wing section tower, and the tower plays the effect of vertical fin, and this tower is called the second tower below as, sets up the second rotor on the second tower.

The second tower is higher than the first tower, and the distance between two towers is greater than the radius of rotor, can reduce the rotor in front and wash the influence of air current to the rotor behind.

The center of a line connecting the centers of rotation of the first rotor and the second rotor is at the center of gravity, and the line overlaps with the longitudinal line of the fuselage.

And the vertical tail wing of the second small tower is provided with a flap which is used for assisting the course control during the rapid horizontal flight.

The blades of each rotor are connected with the rotor shaft through a blade housing, the blade housing is provided with a blade flapping device consisting of a flapping hinge, a shimmy hinge and a variable pitch hinge, and a total pitch and periodic variable pitch controller is arranged to control the pitch change of the rotor blades so as to control the magnitude and direction of the lift force of the rotor.

Each rotor is composed of blades with the same size and the same number, the blades of the rotor are two or more, and the rotor composed of three blades is taken as an example for simplifying the description, and the rotating surface of the rotor is horizontally arranged.

First rotor and second rotor all comprise three paddle, set up rotor synchronizer and make the installation azimuth of one of them paddle of first rotor and second rotor and the contained angle of fuselage longitudinal line aircraft nose direction be 0, even the plane of rotation projection of rotor overlaps at the horizontal plane part, the paddle of rotor also can not collide each other to reduce the height that the towelette needs.

The middle part of the machine body is provided with an upper single wing with a large aspect ratio, the left side and the right side of the upper single wing are respectively provided with a variable propeller pitch propeller, the rotating surface of the variable propeller pitch propeller is vertical to the horizontal plane, the normal line of the rotating surface is parallel to the longitudinal line of the machine body, and the left side and the right side of the upper single wing are provided with flaps for differential auxiliary control of rolling in rapid horizontal flight.

The differential mechanism is characterized in that an engine drives a differential mechanism through a gearbox and a clutch, one output shaft of the differential mechanism drives a synchronous reverser through an overrunning clutch and a cardan shaft, two output shafts of the synchronous reverser are connected with the cardan shaft to respectively drive a first rotor and a second rotor, so that the rotating speeds of the first rotor and the second rotor are the same, the rotating directions are opposite, in addition, the azimuth angles of blades of the first rotor and the second rotor are kept to be synchronously changed, the output shaft of the differential mechanism is hereinafter referred to as a first differential output shaft, the synchronous reverser is hereinafter referred to as a rotor synchronous reverser, a brake is arranged, and the first differential output shaft is braked, and the brake is hereinafter referred to as a first brake.

The other output shaft of the differential drives another synchronous reverser through an overrunning clutch and a universal shaft, two output shafts of the synchronous reverser are connected with the universal shaft to respectively drive a left variable pitch propeller and a right variable pitch propeller, so that the left variable pitch propeller and the right variable pitch propeller have the same rotating speed and opposite rotating directions, the output shaft of the differential is called a differential second output shaft, the synchronous reverser, called a propeller synchronous reverser, is provided with a brake, and the differential second output shaft is braked, and the brake is called a second brake.

An undercarriage is arranged under the fuselage near the center of gravity.

The working principle of the braking differential rotor propeller fixed wing helicopter is as follows: if the rotor adopts three paddle to constitute, set up rotor synchronizer and make the installation azimuth of one of them paddle of first rotor and second rotor be 0 with the contained angle of fuselage longitudinal line aircraft nose direction, even the plane of rotation projection of rotor overlaps at the horizontal plane part, the paddle of rotor also can not collide each other, and reduce the height that the towelette needs, establish first rotor anticlockwise and turn, second rotor clockwise turns, the pulling force of variable pitch screw is forward when establishing variable pitch screw positive pitch, the pulling force of variable pitch screw is backward when the variable pitch screw negative pitch.

The first rotor and the second rotor rotate at the same speed and rotate in opposite directions, and the reactive torques of the two rotors are mutually offset.

The braking differential type rotor propeller fixed wing helicopter has three take-off and landing modes, namely a running take-off and landing mode, a short-distance running take-off and landing mode and a vertical take-off and landing mode.

A sliding and taking-off and landing mode: the throttle of the engine is increased, the engine drives the differential mechanism through the gearbox and the clutch to enable all the rotor wings and the propellers to slightly rotate, the first brake is operated, the first output shaft of the differential mechanism is braked to stop rotating, and the rotor wings continue to rotate inertially due to the overrunning clutch.

Due to the first brake, the first output shaft of the brake differential stops rotating, and the power of the engine is completely output to the second output shaft of the differential to drive the left variable pitch propeller and the right variable pitch propeller to rotate.

The throttle of the engine is continuously increased, the power of the engine is completely output to a second output shaft of the differential mechanism to drive a left variable-pitch propeller and a right variable-pitch propeller to rotate rapidly, simultaneously, the positive pitch of the left variable pitch propeller and the right variable pitch propeller is increased, the tension of the left variable pitch propeller and the right variable pitch propeller drives the braking differential rotor propeller fixed wing helicopter to slide forwards, at this time, the first rotor and the second rotor become autorotation rotors, the braking differential type rotor propeller fixed wing helicopter slides away like a conventional fixed wing aircraft and an autorotation rotor aircraft, when a certain speed is reached, the lift force of the fixed wing and the autorotation first rotor wing and second rotor wing is greater than the weight of the braking differential type rotor propeller fixed wing helicopter, and the braking differential type rotor propeller fixed wing helicopter flies off the ground.

The left wing flap of the fixed wing is controlled to deflect downwards to increase the camber of the left wing, so that the left lift force of the wing is increased, meanwhile, the right wing flap of the fixed wing is controlled to deflect upwards to reduce the camber of the right wing, so that the right lift force of the wing is reduced, and the differential proppropeller fixed wing helicopter is braked to roll rightwards; and meanwhile, the left flap of the fixed wing is controlled to deflect upwards to reduce the camber of the left wing, so that the left lift of the wing is reduced, and the differential gyroplane fixed wing helicopter is braked to roll leftwards to realize roll control.

Because first rotor and second rotor are the rotation when braking differential proprotor fixed wing helicopter and roll, can take the pitch change control roll and the every single move of manipulation rotor: operating the collective pitch and cyclic pitch controllers of the first rotor and the second rotor to tilt to the left, the lift forces of the first rotor and the second rotor to tilt to the left, and braking the differential proprotor fixed-wing helicopter to roll to the left; the total pitch and cyclic pitch controller for operating the first rotor and the second rotor tilts to the right, the lift force of the first rotor and the second rotor tilts to the right, and the braking differential rotor propeller fixed wing helicopter rolls to the right to realize roll control.

Operating the collective pitch and cyclic pitch controllers of the first rotor and the second rotor to tilt forward, the lift forces of the first rotor and the second rotor to tilt forward, and the braking differential proprotor fixed-wing helicopter to tilt forward; the total pitch and cyclic pitch controller for operating the first rotor and the second rotor tilts backwards, the lift force of the first rotor and the second rotor tilts backwards, and the differential rotor propeller braking fixed-wing helicopter tilts backwards to realize pitching control.

The flap of the second small tower vertical tail wing is controlled to deflect leftwards, the lift force of the second small tower vertical tail wing is controlled rightwards, and the braking differential type rotor propeller fixed wing helicopter is driven to turn leftwards; and a wing flap of the second small tower vertical tail wing is controlled to deflect rightwards, the lift force of the second small tower vertical tail wing is controlled leftwards, and the braking differential type rotor propeller fixed wing helicopter is driven to turn rightwards, so that course control is realized.

Heading control can also be achieved by differential pitch of the left variable pitch propeller and the right variable pitch propeller: the pitch of the right variable pitch propeller is controlled to be increased, the tension of the right variable pitch propeller is increased, meanwhile, the pitch of the left variable pitch propeller is controlled to be reduced, the tension of the left variable pitch propeller is reduced, the tension of the right variable pitch propeller and the tension of the left variable pitch propeller generate a left steering moment, and the differential rotor propeller fixed wing helicopter is braked to steer left; and controlling the pitch of the left variable pitch propeller to increase, controlling the tension of the left variable pitch propeller to increase, controlling the pitch of the right variable pitch propeller to decrease, controlling the tension of the right variable pitch propeller and the left variable pitch propeller to generate a rightward steering torque, and controlling the differential rotor propeller to steer the helicopter to the right so as to realize course control.

The pitching, the rolling and the course are effectively controlled, the tension of the left variable-pitch propeller and the right variable-pitch propeller drives the braking differential type rotor propeller fixed-wing helicopter to fly like a conventional fixed-wing helicopter and a self-rotating rotor helicopter, the accelerator of an engine is increased, and the braking differential type rotor propeller fixed-wing helicopter can rapidly and horizontally fly.

When the lift force of the first rotor and the second rotor of the fixed wing and the rotation is smaller than the weight of the braking differential type rotor propeller fixed wing helicopter, the braking differential type rotor propeller fixed wing helicopter descends and lands by using a runway.

Short distance sliding and taking off and landing mode: the engine is throttled up, the engine drives a differential via a gearbox and a clutch to rotate all rotors and propellers slightly, a first brake and a second brake are kept released, and the differential automatically proportionally distributes the power of the engine to the first rotor, the second rotor, a variable-pitch propeller on the left and a variable-pitch propeller on the right.

Continuing to increase the throttle of the engine, the differential automatically proportionally distributes the power of the engine to the first rotor, the second rotor, the left variable-pitch propeller and the right variable-pitch propeller to drive the first rotor and the second rotor to rotate quickly, and also drives the left variable-pitch propeller and the right variable-pitch propeller to rotate quickly, simultaneously increasing the positive pitch of the left variable-pitch propeller and the right variable-pitch propeller, the tension of the left variable-pitch propeller and the right variable-pitch propeller drives the braking differential-rotor-propeller fixed-wing helicopter to slide forward, at this time, the braking differential-rotor-propeller fixed-wing helicopter slides like a conventional fixed-wing aircraft and a conventional helicopter, and when a certain speed is reached, the lift force of the fixed-wing and the power-driven first rotor and the second rotor is greater than the weight of the braking differential-rotor-propeller fixed-wing helicopter In time, the differential-braking rotor-propeller fixed-wing helicopter flies off the ground.

The rotor is driven by power and has larger lift force than the autorotation rotor, so the distance required for sliding is reduced.

The left wing flap of the fixed wing is controlled to deflect downwards to increase the camber of the left wing and increase the lift force of the left wing, and meanwhile, the right wing flap of the fixed wing is controlled to deflect upwards to reduce the camber of the right wing and reduce the lift force of the right wing, so that the differential proppropeller fixed wing helicopter is braked to roll rightwards; and the right wing flap of the fixed wing is controlled to deflect downwards to increase the camber of the right wing, so that the lift force on the right side of the wing is increased, and meanwhile, the left wing flap of the fixed wing is controlled to deflect upwards to reduce the camber of the left wing, so that the lift force on the left side of the wing is reduced, and the differential rotor propeller fixed wing helicopter is braked to roll leftwards to realize roll control.

Because the first rotor and the second rotor are driven to rotate by power, the pitch change of the rotors can be controlled to roll and pitch: operating the collective pitch and cyclic pitch controllers of the first rotor and the second rotor to tilt to the left, the lift forces of the first rotor and the second rotor to tilt to the left, and braking the differential proprotor fixed-wing helicopter to roll to the left; the total pitch and cyclic pitch controller for operating the first rotor and the second rotor tilts to the right, the lift force of the first rotor and the second rotor tilts to the right, and the braking differential rotor propeller fixed wing helicopter rolls to the right to realize roll control.

The pitching, rolling and course are effectively controlled, the tension of the left variable-pitch propeller and the right variable-pitch propeller drives the braking differential type rotor propeller fixed-wing helicopter to fly like a conventional fixed wing helicopter, the accelerator of an engine is increased, and the braking differential type rotor propeller fixed-wing helicopter can fly horizontally and quickly.

When the lift force of the first rotor and the second rotor driven by the fixed wing, the fixed wing and the power is smaller than the weight of the braking differential type rotor propeller fixed wing helicopter, the braking differential type rotor propeller fixed wing helicopter descends and lands in a short distance by using a runway.

The vertical lifting mode: increasing the throttle of the engine, driving the differential mechanism to make all the rotors and the propellers slightly rotate by the engine through the gearbox and the clutch, operating the second brake, stopping the rotation of the second output shaft of the brake differential mechanism, and outputting the power of the engine to the first output shaft of the differential mechanism to drive the first rotor and the second rotor to rotate as the second output shaft of the brake differential mechanism stops rotating, continuing to increase the throttle, increasing the rotating speed of the first rotor and the second rotor, increasing the lift force, when the lift force of the first rotor and the second rotor is larger than the weight of the braking differential rotor propeller fixed wing helicopter, vertically lifting the braking differential rotor fixed wing helicopter, reducing the throttle of the engine, reducing the rotating speed of the first rotor and the second rotor, reducing the lift force, when the lift force of the first rotor and the second rotor is equal to the weight of the braking differential rotor fixed wing helicopter, the braking differential prop-rotor fixed-wing helicopter hovers, continues to reduce the engine throttle, continues to reduce the rotational speed of the first rotor and the second rotor, reduces the lift, and descends vertically when the lift of the first rotor and the second rotor is less than the weight of the braking differential prop-rotor fixed-wing helicopter.

When the braking differential proprotor fixed-wing helicopter is in the air, the total pitch and cyclic pitch controller of the first rotor and the second rotor is controlled to tilt forwards, the lift force of the first rotor and the second rotor tilts forwards, and the braking differential proprotor fixed-wing helicopter tilts forwards; the total pitch and cyclic pitch controller for operating the first rotor and the second rotor tilts backwards, the lift force of the first rotor and the second rotor tilts backwards, and the differential rotor propeller braking fixed-wing helicopter tilts backwards to realize pitching control.

When the braking differential type rotor propeller fixed wing helicopter is in the air, the total pitch and periodic pitch controller of the first rotor and the second rotor are controlled to tilt to the left, the lift force of the first rotor and the second rotor tilts to the left, and the braking differential type rotor propeller fixed wing helicopter rolls to the left; the total pitch and cyclic pitch controller for operating the first rotor and the second rotor tilts to the right, the lift force of the first rotor and the second rotor tilts to the right, and the braking differential rotor propeller fixed wing helicopter rolls to the right to realize roll control.

When the braking differential type rotor propeller fixed wing helicopter is in the air, the second brake is released, the second output shaft of the differential mechanism rotates to drive the left variable pitch propeller and the right variable pitch propeller to rotate, the pitch of the left variable pitch propeller is controlled to be positive, the tension of the left variable pitch propeller is controlled to be forward, meanwhile, the pitch of the right variable pitch propeller is controlled to be negative, the tension of the right variable pitch propeller is controlled to be backward, the tension of the left variable pitch propeller and the right variable pitch propeller generates a right steering moment, and the braking differential type rotor propeller fixed wing helicopter is steered to the right; and controlling the pitch of the right variable pitch propeller to be positive, controlling the tension of the right variable pitch propeller to be forward, simultaneously controlling the pitch of the left variable pitch propeller to be negative, controlling the tension of the left variable pitch propeller to be backward, and controlling the tension of the right variable pitch propeller and the left variable pitch propeller to generate a leftward steering torque, so that the differential-type rotor propeller fixed-wing helicopter is braked to steer leftward, the course control is realized, and when the course is stable, the second output shaft of the differential mechanism is braked by the second brake to stop rotating.

The pitch, roll and course of the differential proprotor fixed wing helicopter are effectively controlled, and the differential proprotor fixed wing helicopter flies like a conventional helicopter.

The differential rotor propeller fixed wing helicopter is controlled to bow forward and increase the throttle, the differential rotor propeller fixed wing helicopter flies forward, the differential rotor propeller fixed wing helicopter is controlled to tilt backward and increase the throttle, and the differential rotor propeller fixed wing helicopter flies backward.

The differential-braking prop-rotor fixed-wing helicopter is controlled to roll rightwards and increase the throttle, the differential-braking prop-rotor fixed-wing helicopter flies rightwards, the differential-braking prop-rotor fixed-wing helicopter is controlled to roll leftwards and increase the throttle, and the differential-braking prop-rotor fixed-wing helicopter flies leftwards.

The engine throttle is reduced, and the differential rotor propeller fixed wing helicopter is braked to vertically and stably descend and land.

A braking differential rotary-wing propeller fixed-wing helicopter flying like a conventional helicopter can be converted to a conventional fixed-wing aircraft plus helicopter mode of flight: the second brake is released and the differential automatically proportionally distributes the power from the engine to the first rotor, the second rotor, and the variable pitch propeller to the left and the variable pitch propeller to the right.

Continuing to increase the accelerator of the engine, the differential automatically proportionally distributes the power of the engine to the first rotor, the second rotor, the left variable-pitch propeller and the right variable-pitch propeller to drive the first rotor and the second rotor to rotate quickly and also to drive the left variable-pitch propeller and the right variable-pitch propeller to rotate quickly, simultaneously increasing the positive pitch of the left variable-pitch propeller and the right variable-pitch propeller, and driving the braking differential-type rotor propeller fixed-wing helicopter to fly quickly and horizontally by the tension of the left variable-pitch propeller and the right variable-pitch propeller, at the moment, the lift force of the fixed wing, the first rotor and the second rotor driven by the power balance the weight of the braking differential-type rotor propeller fixed-wing helicopter, the rotating speed required by the rotors is smaller, the power consumption is less, the efficiency of the propeller is higher than that of the rotor wing due to horizontal forward flight, and the tension of the left variable-pitch propeller and the right variable-pitch propeller drives the braking differential rotor wing propeller to quickly and horizontally fly the fixed-wing helicopter faster than the conventional helicopter.

Can also be converted into a conventional fixed-wing aircraft and autogyro mode for flying: the speed of the fast horizontal flight of the braking differential type rotor-screw fixed-wing helicopter is increased along with the tension of the left variable-pitch propeller and the right variable-pitch propeller, the first brake is operated, the first output shaft of the braking differential mechanism stops rotating, the rotor continues to rotate inertially due to the overrunning clutch, the first output shaft of the braking differential mechanism stops rotating due to the first brake, the power of the engine is completely output to the second output shaft of the differential mechanism to drive the left variable-pitch propeller and the right variable-pitch propeller to rotate more fast, the tension of the left variable-pitch propeller and the right variable-pitch propeller drives the braking differential type rotor-screw fixed-wing helicopter to fast fly forwards, at the moment, the first rotor and the second rotor become autorotation rotors, and the braking differential type rotor-screw fixed-wing helicopter becomes a normal fixed-wing helicopter and autorotation rotor flight mode, the lift of the first rotor of fixed wing and rotation and the weight of the common balanced braking differential formula rotor screw fixed wing helicopter of lift of second rotor, the power consumption of rotor is littleer, because fly before the level, the efficiency of screw is more efficient than the rotor, the pulling force drive braking differential formula rotor screw fixed wing helicopter of a variable pitch screw on the left side and a variable pitch screw on the right flight speed when the quick horizontal flight of variable pitch screw is higher than power drive rotor.

It is also possible to return to normal helicopter mode flight: reducing the engine throttle, slowing down the forward flying speed of the braking differential type gyroplane, loosening the first brake, rotating the first output shaft of the braking differential mechanism to drive the first rotor and the second rotor to rotate, operating the second brake when the lifting force of the first rotor and the second rotor is equal to the weight of the braking differential type gyroplane, stopping the rotation of the second output shaft of the braking differential mechanism, outputting the power of the engine to the first output shaft of the differential mechanism to drive the first rotor and the second rotor to rotate, operating the propeller pitch of the right variable propeller pitch propeller and the left variable propeller pitch propeller to be negative, enabling the braking differential type gyroplane fixed wing helicopter not to fly forward any more, and enabling the braking differential type gyroplane fixed wing helicopter to return to the helicopter mode for flying, reducing the engine throttle, the braking differential type rotor propeller fixed wing helicopter stably descends and lands vertically.

The differential mechanism and the brake are combined to operate to freely distribute the power of the engine to the rotor wing or the variable-pitch propeller, or the rotor wing and the variable-pitch propeller use the power of the engine at the same time, so that the braking differential type rotor wing propeller fixed wing helicopter is easy to fly and change flight modes in three states of a conventional helicopter, a fixed wing aircraft and a self-rotating rotor aircraft, and a fixed wing aircraft and a conventional helicopter, and the variable-pitch propeller is adopted to pull forward to fly, thereby improving the horizontal flight speed and the flight efficiency of the braking differential type rotor wing propeller fixed wing helicopter, being capable of taking off at an airport, reducing the take-off power loss, being free from taking off at the airport vertically, and being suitable for field operation, rapid transportation and the like.

Drawings

The invention is further illustrated with reference to the following figures and examples.

Fig. 1 is a three-dimensional view of a differential proprotor braking fixed wing helicopter of the present invention having three blades.

Fig. 2 is a side view of a differential proprotor braking fixed wing helicopter of the present invention having three blades.

In the figure 1, a first rotor, 2, a second rotor, 3, a left variable pitch propeller, 4, a right variable pitch propeller, 5, a collective pitch and cyclic pitch controller of the first rotor, 6, a collective pitch and cyclic pitch controller of the second rotor, 9, a wing-shaped first tower, 10, a wing-shaped second tower, 11, a second brake, 12, a differential, 13, a first brake, 14, an overrunning clutch and a cardan shaft drive of a synchronous reverser driving the variable pitch propeller, 15, an overrunning clutch and a cardan shaft drive of a synchronous reverser driving the rotor, 16, a synchronous reverser driving the variable pitch propeller (referred to as a propeller synchronous reverser), 17, a synchronous reverser driving the rotor (referred to as a rotor synchronous reverser), 18, a gearbox and a clutch, 19, an engine, 20. fuselage, 22, fixed wing, 25, left wing flap, 26, right wing flap, 29, second pylon vertical tail flap, 30, wheeled landing gear, 31, cardan shaft driving left one variable pitch propeller and right one variable pitch propeller, 32, cardan shaft driving first rotor and second rotor, 33, longitudinal line of fuselage, 121, first output shaft of differential, 122, second output shaft of differential, p, center of gravity.

Detailed Description

In the embodiment shown in fig. 1, two rotors are arranged in a tandem manner, the head of the body (20) is provided with a first wing-shaped tower (9), the first wing-shaped tower (9) plays a role of a vertical tail wing, the first rotor (1) is arranged on the first wing-shaped tower (9), the tail of the body (20) is provided with a second wing-shaped tower (10), the towers play a role of a vertical tail wing, and the second rotor (2) is arranged on the second wing-shaped tower (10).

Set up second small tower (10) and be higher than first small tower (9), the distance is greater than the radius of rotor between two small towers, can reduce the rotor in front and wash the influence of air current to the rotor behind.

The center of the line connecting the centers of rotation of the first rotor (1) and the second rotor (2) is at the center of gravity (P), and the line overlaps the longitudinal line (33) of the fuselage.

The vertical tail of the second small tower (10) is provided with a flap (29) for steering the course during fast horizontal flight.

The blades of each rotor are connected with the rotor shaft through a paddle housing, the paddle housing is provided with a blade flapping device consisting of a flapping hinge, a shimmy hinge and a variable pitch hinge, and a total pitch and periodic variable pitch controller (5) is arranged to operate the pitch change of the blades of the first rotor (1) so as to operate the magnitude and the direction of the lift force of the first rotor (1); the collective and cyclic pitch controller (6) is set to operate the pitch variation of the blades of the second rotor (2) so as to operate the magnitude and direction of the lift force of the second rotor (2).

Each rotor wing is composed of three blades with the same size, and the rotating surface of each rotor wing is horizontally arranged.

The first rotor wing (1) and the second rotor wing (2) are composed of three blades, the rotor wing synchronizing device is arranged to enable the included angle between the installation azimuth angle of one blade of the first rotor wing (1) and the installation azimuth angle of one blade of the second rotor wing (2) and the body direction of the longitudinal line (33) of the airplane body to be 0 degree, even if the rotating plane projection of the rotor wings is partially overlapped on the horizontal plane, the blades of the rotor wings cannot collide with each other, and the height required by the first small tower (9) and the second small tower (10) is reduced.

Fuselage (20) middle part sets up last single wing stationary vane (22) of big aspect ratio, on the left of stationary vane (22), set up variable pitch screw (3) on the left, the rotating plane of variable pitch screw (3) on the left is perpendicular with the horizontal plane, the normal line of rotating plane is parallel with fuselage longitudinal line (33), on stationary vane (22) right, set up variable pitch screw (4) on the left, the rotating plane of variable pitch screw (4) on the right is perpendicular with the horizontal plane, the normal line of rotating plane is parallel with fuselage longitudinal line (33).

A flap (25) is arranged on the left side of the fixed wing (22), and a flap (26) is arranged on the right side of the fixed wing (22) and is used for movably operating the transverse rolling in quick horizontal flight.

An engine (19) is arranged to drive a differential mechanism (12) through a gearbox and a clutch (18), a first output shaft (121) of the differential mechanism drives a synchronous reverser (17) through an overrunning clutch and a cardan shaft (15), referring to fig. 2, two output shafts of the synchronous reverser (17) are connected with a cardan shaft (32) to respectively drive a first rotor (1) and a second rotor (2), the rotating speeds of the first rotor (1) and the second rotor (2) are the same, the rotating directions are opposite, in addition, the azimuth angles of blades of the first rotor (1) and the second rotor (2) are kept synchronously changed, a first brake (13) is arranged to brake the first output shaft (121) of the differential mechanism, a second output shaft (122) of the differential mechanism drives another synchronous reverser (16) through the overrunning clutch and the cardan shaft (14), and two output cardan shafts (31) of the synchronous reverser (16) are respectively connected with a variable propeller pitch (3) on the left side and a variable propeller pitch (3) on the right The variable-pitch propellers (4) enable the left variable-pitch propeller (3) and the right variable-pitch propeller (4) to have the same rotating speed and reverse rotating directions, and a second brake (11) and a second output shaft (122) of a brake differential are arranged.

A wheel type undercarriage (30) is arranged under the fuselage (20) and close to the gravity center (P).

In the figure, an engine (19), a gearbox and a clutch (18), a differential (12), a first output shaft (121) of the differential, a second output shaft (122) of the differential, a first brake (13), a second brake (11), an overrunning clutch and a cardan shaft (15), a synchronous reverser (17), the overrunning clutch and the cardan shaft (14), a synchronous reverser (16), the cardan shaft (31), the cardan shaft (32) and the like are arranged inside a machine body, and are drawn outside the machine body for convenience of display.

The working principle of the braking differential rotor propeller fixed wing helicopter is as follows: and the first rotor wing (1) rotates anticlockwise, the second rotor wing (2) rotates clockwise, the tension of the variable-pitch propeller is forward when the positive pitch of the variable-pitch propeller is set, and the tension of the variable-pitch propeller is backward when the negative pitch of the variable-pitch propeller is set.

The first rotor (1) and the second rotor (2) have the same rotating speed and opposite rotating directions, and the reactive torques of the two rotors are mutually offset.

A sliding and taking-off and landing mode: the throttle of the engine (19) is increased, the engine (19) drives the differential mechanism (12) through the gearbox and the clutch (18) to enable all the rotary wings and the propellers to slightly rotate, the first brake (13) is operated, the first output shaft (121) of the differential mechanism is braked to stop rotating, and the rotary wings further continue to rotate inertially due to the overrunning clutch.

The first output shaft (121) of the braking differential stops rotating due to the first brake (13), and the power of the engine (19) is completely output to the second output shaft (122) of the differential to drive the left variable pitch propeller (3) and the right variable pitch propeller (4) to rotate.

Continuously increasing the accelerator of the engine (19), outputting all the power of the engine (19) to a second output shaft (122) of the differential mechanism to drive a left variable-pitch propeller (3) and a right variable-pitch propeller (4) to rotate quickly, simultaneously increasing the positive pitch of the left variable-pitch propeller (3) and the right variable-pitch propeller (4), driving the braking differential-rotor propeller fixed-wing helicopter to slide forwards by the tension of the left variable-pitch propeller (3) and the right variable-pitch propeller (4), then, the first rotor (1) and the second rotor (2) become autorotation rotors, the braking differential-rotor propeller fixed-wing helicopter slides like a conventional fixed-wing aircraft and an autorotation rotor, and the first rotor (1) and the second rotor (2) become autorotation rotors, when a certain speed is reached, the lift force of the fixed wing (22) and the autorotation first rotor wing (1) and second rotor wing (2) is greater than the weight of the braking differential proprotor fixed wing helicopter, and the braking differential proprotor fixed wing helicopter flies off the ground.

The left wing flap (25) of the fixed wing is operated to deflect downwards to increase the camber of the left wing, so that the left lift force of the fixed wing (22) is increased, meanwhile, the right wing flap (26) of the fixed wing is operated to deflect upwards to reduce the camber of the right wing, so that the right lift force of the fixed wing (22) is reduced, and the differential rotor propeller fixed wing helicopter is braked to roll rightwards; and meanwhile, the left wing flap (25) of the fixed wing is operated to deflect upwards to reduce the camber of the left wing, so that the left lift of the fixed wing (22) is reduced, and the braking differential type gyroplane fixed wing helicopter rolls leftwards to realize roll control.

Because first rotor (1) and second rotor (2) spin when braking differential proprotor fixed wing helicopter and roll, can adopt the pitch change control roll and pitch of manipulation rotor: operating a collective pitch and cyclic pitch controller (5) of a first rotor (1) and a collective pitch and cyclic pitch controller (6) of a second rotor (2) to tilt to the left, the lift forces of the first rotor (1) and the second rotor (2) tilt to the left, and the braking differential proprotor fixed wing helicopter rolls to the left; the total pitch and cyclic pitch controller (5) of the first rotor (1) and the total pitch and cyclic pitch controller (6) of the second rotor (2) are controlled to tilt rightwards, the lift force of the first rotor (1) and the lift force of the second rotor (2) tilt rightwards, and the differential rotor propeller braking fixed wing helicopter rolls rightwards to realize roll control.

Operating a collective pitch and cyclic pitch controller (5) of a first rotor (1) and a collective pitch and cyclic pitch controller (6) of a second rotor (2) to tilt forwards, the lift forces of the first rotor (1) and the second rotor (2) tilt forwards, and a braking differential proprotor fixed wing helicopter tilts forwards; the total distance and periodic distance controller (5) for operating the first rotor wing (1) and the total distance and periodic distance controller (6) for operating the second rotor wing (2) are inclined backwards, the lifting force of the first rotor wing (1) and the lifting force of the second rotor wing (2) are inclined backwards, and the braking differential type rotor wing propeller fixed wing helicopter is inclined backwards to realize pitching control.

A flap (29) of the vertical tail wing of the second small tower is controlled to deflect leftwards, the lift force of the vertical tail wing of the second small tower (10) is controlled to be rightwards, and the braking differential type rotor propeller fixed wing helicopter is driven to turn leftwards; and a flap (29) of the vertical tail wing of the second small tower is controlled to deflect rightwards, the lift force of the vertical tail wing of the second small tower (10) is controlled to be leftwards, and the braking differential type rotor propeller fixed wing helicopter is driven to turn rightwards, so that the course control is realized.

The course control can also be realized by the pitch difference of the left variable pitch propeller (3) and the right variable pitch propeller (4): the pitch of the left variable pitch propeller (3) is controlled to be increased, the tension of the left variable pitch propeller (3) is increased, meanwhile, the pitch of the right variable pitch propeller (4) is controlled to be reduced, the tension of the right variable pitch propeller (4) is reduced, the tension of the left variable pitch propeller (3) and the right variable pitch propeller (4) generates a right steering moment, and the differential speed type rotor propeller fixed wing helicopter is braked to steer to the right; and (3) controlling the pitch of the left variable pitch propeller (3) to be reduced, reducing the tension of the left variable pitch propeller (3), simultaneously controlling the pitch of the right variable pitch propeller (4) to be increased, increasing the tension of the right variable pitch propeller (4), generating a left steering moment by the tension of the left variable pitch propeller (3) and the right variable pitch propeller (4), and braking the differential rotor propeller fixed wing helicopter to steer left to realize course control.

Pitching, rolling and course effective control are realized, the tension of the left variable-pitch propeller (3) and the right variable-pitch propeller (4) drives the braking differential type rotor propeller fixed-wing helicopter to fly like a conventional fixed-wing helicopter and a self-rotating gyroplane, the accelerator of an engine (19) is increased, and the braking differential type rotor propeller fixed-wing helicopter can fly horizontally and rapidly.

When the throttle of the engine is reduced, the lift force of the fixed wing (22) and the autorotation first rotor wing (1) and second rotor wing (2) is less than the weight of the braking differential type rotor propeller fixed wing helicopter, the braking differential type rotor propeller fixed wing helicopter descends and lands by using a runway.

Short distance sliding and taking off and landing mode: the throttle of the engine (19) is increased, the engine (19) drives a differential mechanism (12) through a gearbox and a clutch (18) to enable all the rotors and the propellers to slightly rotate, a first brake (13) and a second brake (11) are kept released, and the differential mechanism (12) automatically distributes the power of the engine (19) to the first rotor (1), the second rotor (2) and the left variable-pitch propeller (3) and the right variable-pitch propeller (4) in proportion.

Continuing to increase the accelerator of the engine (19), the differential mechanism (12) automatically proportionally distributes the power of the engine (19) to the first rotor (1), the second rotor (2), the left variable-pitch propeller (3) and the right variable-pitch propeller (4) to drive the first rotor (1) and the second rotor (2) to rotate rapidly and also drive the left variable-pitch propeller (3) and the right variable-pitch propeller (4) to rotate rapidly, simultaneously, the positive pitches of the left variable-pitch propeller (3) and the right variable-pitch propeller (4) are increased, the tension of the left variable-pitch propeller (3) and the right variable-pitch propeller (4) drives the braking differential-rotor-propeller fixed-wing helicopter to slide forwards, and simultaneously, the total pitch of the first rotor (1) and the second rotor (2) is increased, the lift of the first rotor (1) and the second rotor (2) is increased, at this time, the braking differential proprotor fixed wing helicopter slides away like a conventional fixed wing helicopter plus a conventional helicopter, and when a certain speed is reached, the lift of the fixed wing (22) and the first rotor (1) and the second rotor (2) which are driven by power is greater than the weight of the braking differential proprotor fixed wing helicopter, the braking differential proprotor fixed wing helicopter flies off the ground.

The left wing flap (25) of the fixed wing is controlled to deflect downwards to increase the camber of the left wing, so that the left lift force of the fixed wing (22) is increased, meanwhile, the right wing flap (26) of the fixed wing is controlled to deflect upwards to reduce the camber of the right wing, so that the right lift force of the fixed wing (22) is reduced, and the differential-type gyroplane fixed wing helicopter rolls rightwards; and meanwhile, the left wing flap (25) of the fixed wing is controlled to deflect upwards to reduce the camber of the left wing, so that the left lift of the fixed wing (22) is reduced, and the differential-type gyroplane fixed-wing helicopter is braked to roll leftwards to realize roll control.

Because the first rotor (1) and the second rotor (2) are driven to rotate by power, the pitch change of the rotors can be controlled to roll and pitch: operating a collective pitch and cyclic pitch controller (5) of a first rotor (1) and a collective pitch and cyclic pitch controller (6) of a second rotor (2) to tilt to the left, the lift forces of the first rotor (1) and the second rotor (2) tilt to the left, and the braking differential proprotor fixed wing helicopter rolls to the left; the total pitch and cyclic pitch controller (5) of the first rotor (1) and the total pitch and cyclic pitch controller (6) of the second rotor (2) are controlled to tilt rightwards, the lift force of the first rotor (1) and the lift force of the second rotor (2) tilt rightwards, and the differential rotor propeller braking fixed wing helicopter rolls rightwards to realize roll control.

Operating a collective pitch and cyclic pitch controller (5) of a first rotor (1) and a collective pitch and cyclic pitch controller (6) of a second rotor (2) to tilt forward, the lift forces of the first rotor (1) and the second rotor (2) tilt forward, and the braking differential proprotor fixed wing helicopter tilts forward; the total distance and periodic distance controller (5) for operating the first rotor wing (1) and the total distance and periodic distance controller (6) for operating the second rotor wing (2) are inclined backwards, the lifting force of the first rotor wing (1) and the lifting force of the second rotor wing (2) are inclined backwards, and the braking differential type rotor wing propeller fixed wing helicopter is inclined backwards to realize pitching control.

Pitching, rolling and course effective control are realized, the tension of the left variable-pitch propeller (3) and the right variable-pitch propeller (4) drives the braking differential type rotor propeller fixed wing helicopter to fly like a conventional fixed wing helicopter, the accelerator of an engine is increased, and the braking differential type rotor propeller fixed wing helicopter can fly horizontally and quickly.

When the lift force of the engine accelerator, the fixed wing (22) and the first rotor wing (1) and the second rotor wing (2) driven by power is less than the weight of the braking differential type rotor wing propeller fixed wing helicopter, the braking differential type rotor wing propeller fixed wing helicopter descends and lands in a short distance by using a runway.

The vertical lifting mode: increasing the accelerator of an engine (19), driving a differential mechanism (12) by the engine (19) through a gearbox and a clutch (18) to enable all rotors and propellers to slightly rotate, operating a second brake (11) to brake the second output shaft (122) of the differential mechanism to stop rotating, and because the second output shaft (122) of the differential mechanism stops rotating, all the power of the engine (19) is output to a first output shaft (121) of the differential mechanism to drive a first rotor (1) and a second rotor (2) to rotate, continuously increasing the accelerator of the engine (19), increasing the rotating speed of the first rotor (1) and the second rotor (2), increasing the lift force, and when the weight of the first rotor (1) and the second rotor (2) is larger than that of a differential rotor propeller fixed wing helicopter, vertically lifting the differential rotor propeller fixed wing helicopter and reducing the accelerator of the engine (19), the rotational speed of first rotor (1) and second rotor (2) reduces, lift reduces, when the lift of first rotor (1) and second rotor (2) equals the weight of braking differential rotor propeller fixed wing helicopter, braking differential rotor propeller fixed wing helicopter hovers, continue to reduce the throttle of engine (19), first rotor (1) and second rotor (2) rotational speed continue to reduce, lift reduces, when the lift of first rotor (1) and second rotor (2) is less than the weight of braking differential rotor propeller fixed wing helicopter, braking differential rotor propeller fixed wing helicopter descends perpendicularly.

When the braking differential rotor propeller fixed wing helicopter is in the air, the total distance and cyclic variable distance controller (5) of the first rotor (1) and the total distance and cyclic variable distance controller (6) of the second rotor (2) are operated to incline forwards, the lift forces of the first rotor (1) and the second rotor (2) are inclined forwards, and the braking differential rotor propeller fixed wing helicopter is inclined forwards; the total distance and periodic distance controller (5) for operating the first rotor wing (1) and the total distance and periodic distance controller (6) for operating the second rotor wing (2) are inclined backwards, the lifting force of the first rotor wing (1) and the lifting force of the second rotor wing (2) are inclined backwards, and the braking differential type rotor wing propeller fixed wing helicopter is inclined backwards to realize pitching control.

Because the first rotor (1) and the second rotor (2) are driven to rotate by power, the pitch change of the rotors can be controlled to control roll: operating a collective pitch and cyclic pitch controller (5) of a first rotor (1) and a collective pitch and cyclic pitch controller (6) of a second rotor (2) to tilt to the left, the lift forces of the first rotor (1) and the second rotor (2) tilt to the left, and the braking differential proprotor fixed wing helicopter rolls to the left; the total pitch and cyclic pitch controller (5) of the first rotor (1) and the total pitch and cyclic pitch controller (6) of the second rotor (2) are controlled to tilt rightwards, the lift force of the first rotor (1) and the lift force of the second rotor (2) tilt rightwards, and the differential rotor propeller braking fixed wing helicopter rolls rightwards to realize roll control.

When the braking differential type rotor propeller fixed wing helicopter is in the air, the second brake (11) is released, the differential mechanism second output shaft (122) rotates to drive the left variable pitch propeller (3) and the right variable pitch propeller (4) to rotate, the pitch of the left variable pitch propeller (3) is controlled to be positive, the tension of the left variable pitch propeller () is controlled to be forward, meanwhile, the pitch of the right variable pitch propeller (4) is controlled to be negative, the tension of the right variable pitch propeller (4) is controlled to be backward, the tension of the left variable pitch propeller (3) and the right variable pitch propeller (4) generates a rightward steering moment, and the braking differential type rotor propeller fixed wing helicopter is steered rightward; and controlling the pitch of the right variable pitch propeller (4) to be positive, controlling the tension of the right variable pitch propeller (4) to be forward, simultaneously, controlling the pitch of the left variable pitch propeller (3) to be negative, controlling the tension of the left variable pitch propeller (3) to be backward, and controlling the tension of the right variable pitch propeller (4) and the left variable pitch propeller (3) to generate a leftward steering torque to brake the differential propeller fixed wing helicopter to steer leftward, so that the course control is realized, and when the course is stable, a second output shaft (122) of the differential mechanism is braked by a second brake (11) to stop rotating.

The differential rotor propeller fixed wing helicopter is controlled to bow forward and increase the accelerator of the engine (19), the differential rotor propeller fixed wing helicopter flies forward, the differential rotor propeller fixed wing helicopter is controlled to tilt backward and increase the accelerator of the engine (19), and the differential rotor propeller fixed wing helicopter flies backward.

The differential proprotor fixed wing helicopter is operated to roll right and the accelerator of an engine (19) is increased, the differential proprotor fixed wing helicopter is operated to fly to the right, the differential proprotor fixed wing helicopter is operated to roll left and the accelerator is increased, and the differential proprotor fixed wing helicopter is operated to fly to the left.

A braking differential rotary-wing propeller fixed-wing helicopter flying like a conventional helicopter can be converted to a conventional fixed-wing aircraft plus helicopter mode of flight: when the second brake (11) is released, the differential (12) automatically proportionally distributes the power of the engine (19) to the first rotor (1), the second rotor (2) and the left variable-pitch propeller (3) and the right variable-pitch propeller (4).

Continuing to increase the accelerator of the engine (19), the differential (12) automatically proportionally distributes the power of the engine (19) to the first rotor (1), the second rotor (2), the left variable-pitch propeller (3) and the right variable-pitch propeller (4) to drive the first rotor (1) and the second rotor (2) to rotate rapidly and also drive the left variable-pitch propeller (3) and the right variable-pitch propeller (4) to rotate rapidly, simultaneously, the positive pitches of the left variable-pitch propeller (3) and the right variable-pitch propeller (4) are increased, the tension of the left variable-pitch propeller (3) and the right variable-pitch propeller (4) drives the braking differential-type rotor fixed-wing helicopter to fly rapidly and horizontally, and at the moment, the fixed wing (22) and the first rotor (1) and the second rotor (2) driven by the lift force are jointly balanced to brake the differential-type rotor helicopter The weight of the propeller fixed-wing helicopter is less, the rotating speed required by the rotor is less, the power consumption is less, the efficiency of the propeller is higher than that of the rotor due to horizontal forward flight, and the tension of one variable-pitch propeller (3) on the left and one variable-pitch propeller (4) on the right drive the braking differential type rotor propeller fixed-wing helicopter to quickly and horizontally fly is faster than that of the conventional helicopter.

Can also be converted into a conventional fixed-wing aircraft and autogyro mode for flying: the speed of the fast horizontal flight of the helicopter is increased by driving the braking differential type rotor propeller fixed wing through the tension of the left variable pitch propeller (3) and the right variable pitch propeller (4), the first brake (13) is operated, the first output shaft (121) of the braking differential stops rotating, the rotor continues to rotate inertially due to the overrunning clutch and the cardan shaft drive (15), the first output shaft (121) of the braking differential stops rotating due to the first brake (1), the power of the engine (19) is completely output to the second output shaft (122) of the differential mechanism to drive the left variable pitch propeller (3) and the right variable pitch propeller (4) to rotate more fast, the tension of the left variable pitch propeller (3) and the right variable pitch propeller (4) is increased to drive the braking differential type rotor propeller fixed wing helicopter to fly fast forward, at this time, the first rotor (1) and the second rotor (2) become autorotation rotors, the lift force of the fixed wing (22) and the autorotation first rotor (1) and second rotor (2) balances the weight of the braking differential type rotor propeller fixed wing helicopter, the power consumption of the rotors is smaller, the efficiency of the propellers is higher than that of the rotors due to horizontal forward flight, and the flying speed of the braking differential type rotor propeller fixed wing helicopter is higher than that of the power driven rotors due to the tension driving of the left variable pitch propeller (3) and the right variable pitch propeller (4).

It is also possible to return to normal helicopter mode flight: reducing the throttle of an engine (19), slowing down the forward flying speed of the braking differential proprotor fixed-wing helicopter, loosening a first brake (13), rotating a differential first output shaft (121) to drive a first rotor (1) and a second rotor (2) to rotate, operating a second brake (11) when the lifting force of the first rotor (1) and the second rotor (2) is equal to the weight of the braking differential proprotor fixed-wing helicopter, stopping the rotation of a braking differential second output shaft (122), outputting the power of the engine (19) to the differential first output shaft (121) to drive the first rotor (1) and the second rotor (2) to rotate, operating the propeller pitch of a variable propeller pitch propeller (3) and a variable propeller pitch propeller (4) on the right to be negative, and enabling the braking differential proprotor fixed-wing helicopter to not fly forward any more, the braking differential type rotor propeller fixed wing helicopter returns to the helicopter mode for flying, the accelerator of an engine (19) is continuously reduced, and the braking differential type rotor propeller fixed wing helicopter stably descends and lands vertically.

Claims

1. A braking differential rotor propeller fixed wing helicopter, two rotors adopt a longitudinal arrangement, the head of a helicopter body is provided with a first wing-shaped tower which plays the role of a vertical tail wing, the first tower is provided with a first rotor, the tail of the helicopter body is provided with a second wing-shaped tower which plays the role of a vertical tail wing, the second tower is provided with a second rotor, the second tower is higher than the first tower, the distance between the two towers is larger than the radius of the rotors, the center of a connecting line of the rotating centers of the first rotor and the second rotor is on the gravity center, the connecting line is overlapped with the longitudinal line of the helicopter body, the vertical tail wing of the second tower is provided with a flap which is used for controlling course during fast horizontal flight, the blades of each rotor are connected with the rotor shafts through a blade housing, the blade housing is provided with a swinging hinge, a swinging hinge and a variable pitch hinge, a total pitch and a periodic variable pitch controller are arranged for controlling the change of the blades, thereby controlling the magnitude and direction of the lifting force of the rotor wings, each rotor wing is composed of blades with the same size and the same quantity, the rotating surface of the rotor wing is horizontally arranged, when the rotor wing is composed of three blades, a rotor wing synchronizer is arranged to ensure that the included angle between the initial installation azimuth angle of one blade of the first rotor wing and the aircraft body longitudinal line aircraft nose direction is 0 degree, correspondingly, the included angle between the initial installation azimuth angle of one blade of the second rotor wing and the aircraft body longitudinal line aircraft nose direction is 0 degree, even if the rotating surface projection of the rotor wing is partially overlapped on the horizontal plane, the blades of the rotor wing can not collide with each other, the height required by a small tower is reduced, the middle part of the aircraft body is provided with an upper single-wing fixed wing with a large aspect ratio, the left side and the right side of the fixed wing are respectively provided with a variable propeller pitch, the rotating surface, set up the wing flap in both sides about the fixed wing for move when quick horizontal flight controls the roll, near the focus sets up undercarriage, characterized by under the fuselage: an engine is arranged to drive a differential mechanism through a gearbox and a clutch, a first output shaft of the differential mechanism drives a rotor synchronous reverser through an overrunning clutch and a universal shaft, two output shafts of the rotor synchronous reverser are connected with the universal shaft to respectively drive a first rotor and a second rotor, so that the rotating speeds of the first rotor and the second rotor are the same, the rotating directions are opposite, in addition, the azimuth angles of blades of the first rotor and the second rotor are kept to be synchronously changed, a first brake is arranged to brake the first output shaft of the differential mechanism, the second output shaft of the differential mechanism drives a propeller synchronous reverser through the overrunning clutch and the universal shaft, the two output shafts of the propeller synchronous reverser are connected with the universal shaft to respectively drive a left variable-pitch propeller and a right variable-pitch propeller, so that the rotating speeds of the left variable-pitch propeller and the right variable-pitch propeller, and in the opposite direction, a second brake is arranged to brake a second output shaft of the differential mechanism, the second output shaft of the differential mechanism is controlled by the second brake by utilizing the characteristic of the differential mechanism, all or most of the power of the engine is output to the first rotor and the second rotor so that the braking differential type rotor propeller fixed-wing helicopter works in the conventional helicopter flight mode, the first output shaft of the differential mechanism is controlled by the first brake by utilizing the characteristic of the differential mechanism, all or most of the power of the engine is output to a left variable-pitch propeller and a right variable-pitch propeller, the braking rotor propeller fixed-wing helicopter works in the conventional fixed-wing airplane flight mode by utilizing the tension of the variable-pitch propellers, and the first brake and the second brake are released so that the braking rotor propeller fixed-wing helicopter works in the conventional fixed-wing airplane flight mode of the power-driven rotors during the conventional fixed-wing airplane flight mode, and releasing the second brake, and braking the first output shaft of the differential mechanism by the first brake to enable the braking rotor type propeller fixed wing helicopter to work in a conventional fixed wing aircraft flight mode of a self-rotating rotor.